US7828516B2 - Device for support of an adjusting ring which encompasses at a distance a circular blade carrier - Google Patents

Device for support of an adjusting ring which encompasses at a distance a circular blade carrier Download PDF

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Publication number
US7828516B2
US7828516B2 US11/649,141 US64914107A US7828516B2 US 7828516 B2 US7828516 B2 US 7828516B2 US 64914107 A US64914107 A US 64914107A US 7828516 B2 US7828516 B2 US 7828516B2
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US
United States
Prior art keywords
blade carrier
adjusting ring
levers
lever
ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US11/649,141
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English (en)
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US20070154301A1 (en
Inventor
Martin Hartmann
Alexandra Küpper
Walter Loch
Vadim Shevchenko
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HARTMANN, MARTIN, KUPPER, ALEXANDRA, LOCH, WALTER, SHEVCHENKO, VADIM
Publication of US20070154301A1 publication Critical patent/US20070154301A1/en
Application granted granted Critical
Publication of US7828516B2 publication Critical patent/US7828516B2/en
Expired - Fee Related legal-status Critical Current
Adjusted expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • the invention relates to a device for support of an adjusting ring which encompasses at a distance a basically circular blade carrier, which adjusting ring is rotatable in the circumferential direction around a center axis identical with the blade carrier in order to adjust radially extending stator blades of a ring of a turbo-engine.
  • a device of such type originates, for example, from U.S. Pat. No. 5,549,448.
  • an adjusting ring which is concentric to the center axis of the compressor, encompasses its center casing.
  • Each stator blade of the stator blade ring, which is rotatable around its longitudinal axis, is connected in each case by a pivoted lever to the adjusting ring which is rotatable in the circumferential direction.
  • the rotation of the adjusting ring in the circumferential direction brings about a rotation of the stator blades around the respective longitudinal axis by means of the pivoted lever.
  • the adjusting ring is moved in the circumferential direction by adrive device, which at the same time supports the adjusting ring.
  • the disk spring packs allow a movement of the adjusting ring in the axial direction on account of the axial forces which arise from the reaction forces of the adjustable blades. This leads on one hand to flow losses in the compressor on account of the asymmetrically or differently adjusted stator blades of the ring, as the case may be, when viewed over the circumference, and on the other hand also leads to wear on the support of the adjusting ring and also on the adjusting ring itself.
  • the object of the present invention is the creation of a wear-free and reliable device for support of an adjusting ring, which encompasses at a distance a basically circular blade carrier, for adjusting the radially extending blades of a ring which are rotatable around their longitudinal axis.
  • the device provides a plurality of single-arm levers between the blade carrier and the adjusting ring, which levers are distributed over the circumference, extend tangentially in each case, and which on their free ends have a rotatable roller in each case, which are rollable in the circumferential direction on the adjusting ring or on the blade carrier.
  • the single-arm levers which are flexible in the radial direction, the previously possible movability of the adjusting ring in the axial direction is suppressed since the lever, which is clamped tightly on one side, has an especially high rigidity in the axial direction.
  • the levers can absorb and compensate the axial forces which arise from the reaction forces of the adjustable stator blades without additional constructional elements, such as disk springs, holders or guide elements.
  • a support for the adjusting ring which enables only a rotational movement of the adjusting ring which is orientated in the circumferential direction, and which suppresses a tilting or partial displacement, as the case may be, in the axial direction.
  • wear on the adjusting ring, on the fastening of the single-arm levers, and on the rotatable rollers, which are rollable in the circumferential direction on the adjusting ring or on the blade carrier is avoided.
  • a constantly symmetrical adjustment of the blades of a ring of a turbo-engine is ensured so that no losses occur in the medium which flows around the blades of the ring of the turbo-engine.
  • the efficiency of the turbo-engine is permanently maintained.
  • each lever which faces away from the roller is tightly clamped, for example, on the blade carrier and the roller, which is rotatably mounted on it, is rollable on the inner side of the adjusting ring.
  • the lever in the circumferential direction is fastened tangentially on the blade carrier.
  • the lever can then be simply formed as a strut or a transverse beam which is rectangular in cross section.
  • the rotatably mounted roller is provided on the second free ends of the levers in each case, which roller in this case is rollable on the inner side of the adjusting ring, i.e. on its inner circumferential surface.
  • each roller is rotatable around a roller axis which is parallel to the center axis. This enables the use of cylindrical surfaces on the adjusting ring or on the blade carrier, upon which similarly cylindrical rollers are rollable.
  • each lever is expediently screwed to the blade carrier so that an especially simple fitting and removal of the lever or levers, as the case may be, on the blade carrier is possible.
  • each lever has at least one elongated hole, which extends in the tangential direction, for accommodating the screwed fitting.
  • annular groove is provided on the inner side of the adjusting ring, with a groove base upon which the rollers are rollable.
  • the groove walls of the annular groove guide the rollers and so prevent the slipping off of the rollers from the bearing surface.
  • the device for support of an adjusting ring is especially advantageously usable in a turbo-engine, for example in an axial compressor, including a multi-stage axial compressor, if applicable, wherein the drive for adjusting the blades has an adjusting ring which encompasses the blade carrier, which adjusting ring is supported as claimed in one of the claims.
  • the blades can be formed as stator blades or also as adjustable inlet guide vanes of a compressor. Also, the invention could be used in a steam turbine which has adjustable inlet guide vanes or stator blades.
  • FIG. 1 shows a gas turbine with a compressor in a longitudinal partial cross section
  • FIG. 2 shows a roller block, which is clamped on one side, for support of the adjusting ring.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. Inside, it has a rotor 3 , which is also designated as a turbine rotor, which is rotatably mounted around a rotational axis 2 .
  • the annular combustion chamber 6 forms a combustion space 17 which communicates with an annular hot gas passage 18 .
  • There, four turbine stages 10 which are connected one behind the other, form the turbine unit 8 . Each turbine stage 10 is formed from two blade rings.
  • a row 14 which is formed from rotor blades 15 follows a stator blade row 13 in each case in the hot gas passage 18 .
  • the stator blades 12 are fastened on the stator, whereas the rotor blades 15 of a row 14 are attached on the rotor 3 by means of a turbine disk.
  • a generator or a driven machine (not shown) is coupled to the rotor 3 .
  • Adjustable inlet guide vanes 19 are provided at the inlet of the compressor 5 on the intake duct side.
  • the inlet guide vanes 19 are arranged radially in the annular flow passage of the compressor 5 and can be rotated around their respective longitudinal axis by a drive device 21 in order to adjust the mass flow which flows through the gas turbine 1 .
  • a drive device 21 in order to adjust the mass flow which flows through the gas turbine 1 .
  • an especially large or a small mass flow can flow through the gas turbine 1 to satisfy demands.
  • the drive is effected by an adjusting ring 26 which encompasses the casing of the compressor 5 , and which is coupled by levers 25 to the inlet guide vanes 19 .
  • the adjusting ring 26 is rotatable in the circumferential direction around the center axis 24 .
  • FIG. 2 shows a detail from a cross section through the compressor 5 according to the section line II in the region of the blade carrier 22 .
  • the blade carrier 22 which is formed as a stator blade carrier, is basically circular in cross section and is encompassed by the adjusting ring 26 which is concentric to its center axis 24 .
  • the adjusting ring 26 serves for the drive of radially extending inlet guide vanes 19 of the compressor 5 , the blade airfoils of which form in the annular flow passage of the compressor 5 a ring-shaped blade cascade for adjustment of the mass flow.
  • the device for support of the adjusting ring 26 can also be used or provided, as the case may be, for an adjusting ring 26 which is used for the drive of adjustable stator blades of the compressor 5 .
  • a plurality of single-arm levers 27 are provided, which are distributed over the circumference of the blade carrier 22 , which levers have a tightly clamped end 28 and a free end 30 which lies opposite this.
  • the fixed end 28 of the lever 27 is screwed on the support side, i.e. on the blade carrier 22 .
  • two commercially available screws 42 are used for this purpose, which rigidly connect the clamped end 28 to the blade carrier 22 .
  • a roller 32 is provided on the free end 30 of the lever 27 , the rotational axis 34 of which is oriented parallel to the center axis 24 .
  • the adjusting ring 26 on its inner side 36 has an endlessly encompassing annular groove 38 in which each roller 32 of the device engages so that these are rollable on the groove base 40 of the annular groove 38 .
  • Each lever 27 is designed in its dimensions in such a way that this presses the roller 32 , which is rotatably mounted on its free end 30 , under a pretensioning onto the inner side 36 or onto the groove base 40 of the annular groove 38 , as the case may be.
  • the measure h can be specified, which describes the spacing of the rotational axis 34 between pretensioned position and relaxed position, i.e. without adjusting ring 26 .
  • the device preferably has an odd number, for example five or seven, of such levers 27 , in order to mount the adjusting ring 26 concentrically around the center axis 24 .
  • An even number of levers 27 is also conceivable.
  • Each lever 27 which is also designated as a roller block, has on its fixed end 28 on the support side at least one elongated hole 44 for one or preferably more screws 42 .
  • the lever 27 is movable in the tangential direction before screwing down so that the spacing of the rotational axis 34 and center axis 24 , viewed in the radial direction, can be adjusted, as a result of which the magnitude of the pretensioning by which the lever 27 presses the roller 32 onto the inner side 36 of the adjusting ring 26 or onto the groove base 40 , as the case may be, can be especially simply adjusted.
  • the use of two or more screws 42 prevents a twisting of the lever 27 around its radial axis, for example around the longitudinal axis of a screw.
  • all levers 27 which are distributed over the circumference have the same pretensioning in order to concentrically support the adjusting ring 26 .
  • rollers 32 which are guided in an endlessly encompassing annular groove 38 , the axial width of which rollers corresponds approximately to the width of the annular groove 38 , reliably prevent a tilting of the adjusting ring 26 or its axial displacement, as the case may be.
  • the rollers 32 which are guided by the groove walls, guide the adjusting ring 26 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Coating Apparatus (AREA)
  • Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
  • Grinding Of Cylindrical And Plane Surfaces (AREA)
  • Processing Of Stones Or Stones Resemblance Materials (AREA)
  • Tyre Moulding (AREA)
  • Manufacture Of Motors, Generators (AREA)
US11/649,141 2006-01-02 2007-01-03 Device for support of an adjusting ring which encompasses at a distance a circular blade carrier Expired - Fee Related US7828516B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06000027 2006-01-02
EP06000027A EP1803902B1 (de) 2006-01-02 2006-01-02 Vorrichtung zur Abstützung eines einen kreisförmigen Schaufelträger beabstandet umgreifenden Stellrings
EP06000027.0 2006-01-02

Publications (2)

Publication Number Publication Date
US20070154301A1 US20070154301A1 (en) 2007-07-05
US7828516B2 true US7828516B2 (en) 2010-11-09

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Family Applications (1)

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US11/649,141 Expired - Fee Related US7828516B2 (en) 2006-01-02 2007-01-03 Device for support of an adjusting ring which encompasses at a distance a circular blade carrier

Country Status (4)

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US (1) US7828516B2 (de)
EP (1) EP1803902B1 (de)
AT (1) ATE403798T1 (de)
DE (1) DE502006001275D1 (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130216360A1 (en) * 2012-02-21 2013-08-22 Mitsubishi Heavy Industries, Ltd. Axial-flow fluid machine, and variable vane drive device thereof
US9651053B2 (en) 2014-01-24 2017-05-16 Pratt & Whitney Canada Corp. Bleed valve
US9915149B2 (en) 2015-08-27 2018-03-13 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier on the low pressure side of a fan blade
US9976514B2 (en) 2015-08-27 2018-05-22 Rolls-Royce North American Technologies, Inc. Propulsive force vectoring
US10125622B2 (en) 2015-08-27 2018-11-13 Rolls-Royce North American Technologies Inc. Splayed inlet guide vanes
US10233869B2 (en) 2015-08-27 2019-03-19 Rolls Royce North American Technologies Inc. System and method for creating a fluidic barrier from the leading edge of a fan blade
US10267159B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North America Technologies Inc. System and method for creating a fluidic barrier with vortices from the upstream splitter
US10267160B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US10280872B2 (en) 2015-08-27 2019-05-07 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier from the upstream splitter
US10718221B2 (en) 2015-08-27 2020-07-21 Rolls Royce North American Technologies Inc. Morphing vane
US10947929B2 (en) 2015-08-27 2021-03-16 Rolls-Royce North American Technologies Inc. Integrated aircraft propulsion system

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20120101664A (ko) * 2009-11-30 2012-09-14 제랄드 엘. 바버 조정 가능한 발전기를 구비한 풍력 터빈
IT1401664B1 (it) 2010-08-31 2013-08-02 Nuova Pignone S R L Dispositivo di centraggio e sistema per anello di guida.
DE102011086031B4 (de) * 2010-11-23 2016-02-04 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable Turbinengeometrie
CN111373155B (zh) 2017-09-25 2022-09-02 江森自控科技公司 紧凑可变几何形状的扩散器机构
CN114961882A (zh) * 2021-02-26 2022-08-30 中国航发商用航空发动机有限责任公司 可调静子叶片角度控制装置

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US3558237A (en) * 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
US3736070A (en) 1971-06-22 1973-05-29 Curtiss Wright Corp Variable stator blade assembly for axial flow, fluid expansion engine
US3841788A (en) * 1972-10-28 1974-10-15 J Sljusarev Device for turning the stator vanes of turbo-machines
DE2513581A1 (de) 1975-03-06 1976-09-09 Bbc Brown Boveri & Cie Turbinenregelung eines heizkraftwerkes
US3990809A (en) * 1975-07-24 1976-11-09 United Technologies Corporation High ratio actuation linkage
US4035101A (en) 1976-03-24 1977-07-12 Westinghouse Electric Corporation Gas turbine nozzle vane adjusting mechanism
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
US5035572A (en) 1989-04-21 1991-07-30 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for adjusting guide blades
US5538214A (en) * 1994-07-27 1996-07-23 Sinila; Alexander Locking accessory support apparatus
US5549448A (en) 1995-02-08 1996-08-27 United Technolgies Corporation Variable stator vane linkage system and method
US20030165384A1 (en) * 2000-11-15 2003-09-04 Volvo Aero Corporation Gas turbine stator
EP1524413A2 (de) 2003-10-15 2005-04-20 United Technologies Corporation Lagerbuchse aus Elektrographit für eine verstellbare Leitschaufel
DE10351202A1 (de) 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3558237A (en) * 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
US3736070A (en) 1971-06-22 1973-05-29 Curtiss Wright Corp Variable stator blade assembly for axial flow, fluid expansion engine
US3841788A (en) * 1972-10-28 1974-10-15 J Sljusarev Device for turning the stator vanes of turbo-machines
DE2513581A1 (de) 1975-03-06 1976-09-09 Bbc Brown Boveri & Cie Turbinenregelung eines heizkraftwerkes
US3990809A (en) * 1975-07-24 1976-11-09 United Technologies Corporation High ratio actuation linkage
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
US4035101A (en) 1976-03-24 1977-07-12 Westinghouse Electric Corporation Gas turbine nozzle vane adjusting mechanism
US5035572A (en) 1989-04-21 1991-07-30 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for adjusting guide blades
US5538214A (en) * 1994-07-27 1996-07-23 Sinila; Alexander Locking accessory support apparatus
US5549448A (en) 1995-02-08 1996-08-27 United Technolgies Corporation Variable stator vane linkage system and method
US20030165384A1 (en) * 2000-11-15 2003-09-04 Volvo Aero Corporation Gas turbine stator
EP1524413A2 (de) 2003-10-15 2005-04-20 United Technologies Corporation Lagerbuchse aus Elektrographit für eine verstellbare Leitschaufel
DE10351202A1 (de) 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130216360A1 (en) * 2012-02-21 2013-08-22 Mitsubishi Heavy Industries, Ltd. Axial-flow fluid machine, and variable vane drive device thereof
US9284851B2 (en) * 2012-02-21 2016-03-15 Mitsubishi Heavy Industries, Ltd. Axial-flow fluid machine, and variable vane drive device thereof
US9651053B2 (en) 2014-01-24 2017-05-16 Pratt & Whitney Canada Corp. Bleed valve
US9915149B2 (en) 2015-08-27 2018-03-13 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier on the low pressure side of a fan blade
US9976514B2 (en) 2015-08-27 2018-05-22 Rolls-Royce North American Technologies, Inc. Propulsive force vectoring
US10125622B2 (en) 2015-08-27 2018-11-13 Rolls-Royce North American Technologies Inc. Splayed inlet guide vanes
US10233869B2 (en) 2015-08-27 2019-03-19 Rolls Royce North American Technologies Inc. System and method for creating a fluidic barrier from the leading edge of a fan blade
US10267159B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North America Technologies Inc. System and method for creating a fluidic barrier with vortices from the upstream splitter
US10267160B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US10280872B2 (en) 2015-08-27 2019-05-07 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier from the upstream splitter
US10718221B2 (en) 2015-08-27 2020-07-21 Rolls Royce North American Technologies Inc. Morphing vane
US10947929B2 (en) 2015-08-27 2021-03-16 Rolls-Royce North American Technologies Inc. Integrated aircraft propulsion system

Also Published As

Publication number Publication date
US20070154301A1 (en) 2007-07-05
EP1803902A1 (de) 2007-07-04
DE502006001275D1 (de) 2008-09-18
EP1803902B1 (de) 2008-08-06
ATE403798T1 (de) 2008-08-15

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